56756 Federal Register / Vol. 77, No. 179 / Friday, September 14, 2012 / Rules and Regulations 

rotating star, part number (P/N) 

341A31.4116.21, installed on Model 

SA341G helicopters. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, DGAC, its 

technical representative, has notified us 

of the unsafe condition described in the 

DGAC AD. We are issuing this AD 

because we evaluated all information 

provided by DGAC and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type designs and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

21 helicopters of U.S. registry and the 

actions will take approximately 6 work 

hours per helicopter to accomplish at an 

average labor rate of $85 per work hour. 

Required parts will cost approximately 

$6,000. Based on these figures, we 

estimate the total cost impact of this AD 

on U.S. operators to be $6,510 to replace 

the rotating star on each helicopter, or 

$136,710 for the entire U.S. fleet. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–17–09 Eurocopter France: 

Amendment 39–17172; Docket No. 

FAA–2012–0338; Directorate Identifier 

2009–SW–51–AD. 

(a) Applicability 

This AD applies to Model SA341G 

helicopters, with rotating star, part number 

(P/N) 341A31.4116.21 installed, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

reduced service life of the rotating star. This 

condition could result in failure of the 

rotating star and subsequent loss of control 

of the helicopter. 

(c) Effective Date 

This AD becomes effective October 19, 

2012. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(e) Required Actions 

(1) Before further flight, remove any 

rotating star, P/N 341A31.4116.21, with 

12,000 or more hours time-in-service (TIS), 

and replace it with an airworthy rotating star 

with less than 12,000 hours TIS. 

(2) Revise the Airworthiness Limitations 

section of the Instructions for Continued 

Airworthiness by reducing the service life of 

the main rotor rotating star from unlimited 

hours TIS to 12,000 hours TIS. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

Direction Generale de l’Aviation Civile 

(France) AD No. F–2004–070, dated May 26, 

2004. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220: Main Rotor Head. 

Issued in Fort Worth, Texas, on August 21, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21531 Filed 9–13–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0008; Directorate 

Identifier 2011–NE–43–AD; Amendment 39– 

17115; AD 2012–14–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 


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Federal Register / Vol. 77, No. 179 / Friday, September 14, 2012 / Rules and Regulations 56757 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) BR700–715A1–30, BR700– 

715B1–30, and BR700–715C1–30 

turbofan engines. This AD was 

prompted by the discovery of a 

manufacturing defect on certain part 

number (P/N) and serial number (S/N) 

low-pressure (LP) compressor booster 

rotors. This AD requires initial and 

repetitive fluorescent penetrant 

inspections of certain P/N and S/N LP 

compressor booster rotors and rework or 

replacement of them as terminating 

action to the repetitive inspections. We 

are issuing this AD to prevent failure of 

the LP compressor booster rotor, 

uncontained engine failure, and damage 

to the airplane. 

DATES: This AD becomes effective 

October 19, 2012. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

October 19, 2012. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7758; fax: 781–238– 

7199; email: mark.riley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on February 24, 2012 (77 FR 

11019). That NPRM proposed to correct 

an unsafe condition for the specified 

products. European Aviation Safety 

Agency (EASA) AD 2011–0232 states: 

Several LP compressor booster rotors have 

been found non-compliant to original design. 

The technical investigations carried out by 

Rolls-Royce Deutschland revealed that this 

discrepancy is due to a manufacturing defect 

and that only some specific LP compressor 

booster rotor serial numbers are affected. 

This condition, if not corrected, could lead 

to an uncontained engine failure, potentially 

damaging the aeroplane and injuring its 

occupants, and/or injuring persons on the 

ground. 

To address this condition, RRD has 

developed an inspection program and a 

rework for the affected LP compressor 

booster rotors. 

For the reason described above, depending 

on engine type of operations, this AD 

requires repetitive fluorescent penetrant 

inspections of the LP compressor booster 

rotor and if any crack is found, replacement 

with a serviceable part. This AD also requires 

rework of all affected LP compressor booster 

rotors. 

You may obtain further information by 

examining EASA AD 2011–0232 in the 

AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects about 96 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 5 work-hours per engine to 

perform one inspection and about 8 

work-hours per engine to perform the 

rework. The average labor rate is $85 per 

work-hour. Based on these figures, if all 

engines are reworked, we estimate the 

cost of the AD on U.S. operators to 

perform one inspection and to perform 

the rework to be $106,080. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–14–01 Rolls-Royce Deutschland Ltd & 

Co KG: Amendment 39–17115; Docket 

No. FAA–2012–0008; Directorate 

Identifier 2011–NE–43–AD. 

(a) Effective Date 

This AD becomes effective October 19, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG (RRD) BR700– 


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715A1–30, BR700–715B1–30, and BR700– 

715C1–30 turbofan engines, with a lowpressure (LP) compressor booster rotor, part 

number (P/N) BRH19215, or P/N BRH19871, 

with serial numbers (S/N) 118 to 255 

inclusive, installed. 

(d) Reason 

This AD was prompted by the discovery of 

a manufacturing defect on certain P/N and S/ 

N LP compressor booster rotors. We are 

issuing this AD to prevent failure of the LP 

compressor booster rotor, uncontained 

engine failure, and damage to the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(1) At the applicable compliance time in 

Table 1 to paragraph (e) of this AD, perform 

an initial fluorescent penetrant inspection 

(FPI) of the LP compressor booster rotor, in 

accordance with paragraphs 3.D. through 

3.H.(1) (except paragraphs 3.G.(1) and 

3.G.(2)) of Accomplishment Instructions of 

RRD Alert Non-Modification Service Bulletin 

No. ALERT SB–BR700–72–A900503, 

Revision 4, dated June 16, 2011. 

TABLE 1 TO PARAGRAPH (E)—COMPLIANCE TIMES

Engine type of operation Initial FPI (whichever occurs later) 

Repetitive FPI 

interval 

(not to exceed) 

‘‘Hawaiian’’ Flight Mission only ................................................. Before accumulating 36,000 engine cycles (EC) or within 500 

EC after the effective date of this AD.

6,000 EC 

Any other rating, or combination of ratings .............................. Before accumulating 18,000 EC, or within 500 EC after the 

effective date of this AD.

4,000 EC 

(2) Thereafter, at intervals not to exceed the 

applicable compliance time in Table 1 of this 

AD, perform repetitive FPIs of the LP 

compressor booster rotor, in accordance with 

paragraphs 3.D. through 3.H.(1) (except 

paragraphs 3.G.(1) and 3.G.(2)) of 

Accomplishment Instructions of RRD Alert 

Non-Modification Service Bulletin No. 

ALERT SB–BR700–72–A900503, Revision 4, 

dated June 16, 2011. 

(3) Remove cracked LP compressor booster 

rotors before further flight. 

(4) At the next piece part exposure of the 

LP compressor booster rotor during shop 

visit, remove the LP compressor booster rotor 

and either: 

(i) Rework the LP compressor booster rotor 

in accordance with paragraph 3.D. of 

Accomplishment Instructions of RRD Service 

Bulletin (SB) No. SB–BR700–72–101683, 

dated September 20, 2010; or 

(ii) Replace the LP compressor booster 

rotor with one that is eligible for installation. 

(f) Definitions 

(1) For the purpose of this AD, an LP 

compressor booster rotor that is eligible for 

installation is one that is not listed in 

applicability paragraph (c) of this AD. 

(2) The Hawaiian Flight Mission referenced 

in Table 1 to paragraph (e) is shown in Figure 

1 to paragraph (f)(2): 


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(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(h) Related Information 

(1) For more information about this AD, 

contact Mark Riley, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7758; fax: 781–238–7199; 

email: mark.riley@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0232, dated December 13, 2011, for related 

information. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise: 

(i) Rolls-Royce Deutschland (RRD) Ltd & 

Co KG Alert Non-Modification Service 

Bulletin No. ALERT SB–BR700–72–A900503, 

Revision 4, dated June 16, 2011. 

(ii) RRD Ltd & Co KG Service Bulletin No. 

SB–BR700–72–101683, dated September 20, 

2010. 

(3) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlewitz, 15827 

Blankenfelde-Mahlow, Germany, telephone: 

+49 (0) 33–7086–1883, fax: +49 (0) 33–7086– 

3276. 

(4) You may review this service 

information at the FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

(5) You may also review the service 

information that is incorporated by reference 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

June 25, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22533 Filed 9–13–12; 8:45 am] 

BILLING CODE 4910–13–P 


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